Airplane-fuselage



W. L. GILMORE.

AIRPLANE FUSELAGE.

APPLICATION FILED 050.21.1920.

1,394,796 Patented 00a. 25, 1921.

2 SHEETS-SHEET I.

FIG.

amoemtoz WELMFW? L. GHLMOFIE' new rates treat sates- WELIAEEI L; GEMOBE,OF PORT WGI'ON, NEW YORK, ASSIGNOB, BY MESNE ASSIGNMENTS, T CUBTISSAEPLANE AND MOTOR CORPORATION, OF BUFFALO,

NEW YORK, COREORATION OF NEW YORK.

marLmrn-susnnaen nseaaac.

Specification of Letters latent.

Patented Oct. 25, real.

original application filed June 11, 1919, Serial No. 303,561. Dividedand this application filed December- 27, 1920. Serial No. 433,090.

' Port Washington, in the county of Nassau and State of New York, haveinvented certam new and useful Improvements in Airplane-Fuselage, ofwhich the following is a specification.

My invention relates t airplane bodies of the monocoque type and is adivision of application Serial No. 303,501, filed June. 11, 1919.

- In construction monocoque bodies or shells it 'is the presentpractice, as distinguished from the invention herein disclosed, toconstruct the fuselage or nacelle of a plurality of layers of spirallylaid strips of wood. These strips of wood are placed edge to edge andspiraled diagonally throughout the full circumference of the shell. Togive the shell strength the strips of one layer are spiraled oppositelyor at an angle to the strips ofthe other and between the oppositelyspiraled layers a third or reinforcing layer of strips is interposed.The strips of the third or reinforcing layer extend longi tudinally ofthe shell and constitute the mean relied upon to prevent its axialdistortion. In its manufacture the strips of the inner and outer layersare spiraled di-' agonally and continuously around a suitable core orfiller and uponthecompletion of the shell the core or filler, which ispreferably of the knock-down type, is removed or withdrawn in sections.Subsequent to its completion, and then only, can the installation of theinterior fuselage equipment begin. Accordingly, a fuselage thuscharacterized and constructed is exceedingly poor and extremely costlyfrom a production point of view. Moreover, the shell is heavy and out ofall proportions to its strength.

The present invention aims to, and does overcome the above mentionedobjectionable features. Instead of carrying the spirally laid strips ofwood completely and continu ously around the body a differentarrangement is followed. The body or shell is preferably made in halves.The halves of the body are s' :arly constructed and when completed arearranged edge to edge with. their open or concave sides adjacent. Eachhalf or shell section comprises but two layers (an inner and an outer)of spirally laid strips, the strips constituting the respective layersbeing spiraled opposite to each other. In addition to this the strips ofboth layers of one half or section are spiraled oppositely to the stripsof the corresponding layers of the other section. It is this latterarrangementfl. e., the difierence' in arrangement of the layer or layersof the longitudinally divided halves that I rely upon to eliminate thetwisting moment set up in .fusela-ges or nacelles wherein the stripsconstituting the shell or body are carried throughout the fullcircumference or completely around the fuselage or nacelle. By

- placing the longitudinal edges of the two halves iu abuttingengagement the twisting tendency of the one half is counteracted by theopposite twisting tendency oft-he other. The use of a third oradditional layer is unnecessary.

In the construction of the improved fuselage or nacelle a core or fillerof a size and shape in cross section approximately the same as the sizeand shape in cross section of one half of the body, is provided. Uponthe rounded surface of the core 'a series or plurality of strips arespirally laid, the ends of the strips being extended beyond the fiat ornon-working face of the core Where they are temporarily fastened andl1eld. This having been done a second series of strips is laid andfastened down upon the series of strips first mentioned. In laying saidsecond series the strips are glued to the first mentioned layer ofstrips and extended diagonally in the opposite direction. The two.

series of strips together constitute a complete shell section or half.After drying a-nd setting the shell section is removed by cutting (m amanner hereinafter more fully explained) and immediately upon itsremoval, or during its construction the Second 1 simultaneously engagedin the work.

or shell section first constructed is placed with its open or concaveside uppermost to admit of the subsequent installation of such interiorfuselage equipment and structural elements as the frames, as tank,motors, etc.

Duringtheinstallation of the interior equip-- .ment a large number ofworkmen ma be eretofore, as intimated, the number of workmenthusengaged. has been limited to one or ossibly two (in the average sizemachine or uselage) due to the fact that such work must be done afterthe shell is-complete and hence entirely from the inside. In the lattercase-it also becomes necessary for the workman or workmen to carry onthe work in a more or less cramped position. Upon the completion of theassembly of the interior equipment, and not until then is the remainingor second half or shell section fitted in place. In fittlng it, thesecond shell section is placed with its longitudinal edges in abuttingengagement with the corresponding edges thereof. A'fter trimming or'cutting.

off the abutting edges to provide a perfect fit the two shell sectionsare fas'tenedtogether and removed from the jig with the interiorfuselage equipment completely assembled and intact.

In addition to the advantages above noted other advantages and improvedresults will be noted hereinafter. The scope of the invention will befound," however, upon refer ence to the appended claims.

Of the drawings, wherein like characters of reference'designate like orcorresponding parts;

Figu

vertical section and partly in side elevation, of the core or fillerover which one or both sections of the monocoque shell are formed. Inthis v ew a portion of one of the sections is shown fastened to the jigupon and to which the core or filler is attached;

' Fig. 2 1s a similar view of the jig or stand upon whlch thefinished-half sections of the shell. are assembled. In this view one ofthe half sections is shown resting on the stand with a portion of theinterior equipment of the fuselage assembled;

Fig. 3 is'a transverse vertical section of the construction jig andcore. Here again a portion of one of the shell sections is shown;

Fig. 4 is a transverse vertical section of the assembly jig. or stand.In this view, as in Fig. 2, one of the half sections and one of theelements 0? the interior fuselage equipment is shown Fig. 5 is a plan'view of the fuselage as it re 1 is a view, partly in longitudinalappears. in its relation to an airplane. -In thisview as in previousviews, portions of the shell Have been removed to better illustrate themanner in which the fuselage is constructed, and

- Fig. 6 is a detail fragmentary view illustratinga modified arrangementof the strips of wood constituting t e respective shell sections orhalves.

\ In the embodiment of the invention se-' lected for illustration afuselage of more or less conventional shape is disclosed. Being of themonocoque type 'it is characterized by an ovoidal cross sectionthroughout sub- .stantially its full length. 4 The shape of thetudinally throughout the full length of the body as indicated at 11.They, the halves,

are of identical construction and where the body is divided verticallythe shape of the abutting halves is exactly the same. fEach halfcomprises an inner and an outer layer of. spirally laid strips of wood.The outer layer designated as 12 comprises stripsbf wood laid edge to edand spiraled diagonally at an angle. he'inner layer designated as 13,likewise comprises strips of wood laid edge to edge although the stripsin this instance, vwhile spiraled diagonally and at an angle arespiraled oppositely or at substantially a right angle to the strips ofthe layer 12. The direction in which the strips of the respective layersare spiraled is immaterial, it being only essential that they beoppositely spiraled for increased strength. While the strips of theouter layer 12 of one shell section are spiraled at an angle to thestrips of the inner layer 13 of the same shell section, the strips ofthe outer layer 12 of the one shell section are spiraled in the samedirection as the striped the inner layer 13 of the other or remainingshell section. In other words, the layers of strips constituting theouter shell sections are spiraled oppositely to each other as are thestrips constituting the inner layers. In Fig; 5 of the drawings therelative arrangement of the strips of wood may be noted.

By extending the strips of the respective layers of one section at anangle to each' ot er and by extending the strips of the correspondinglayers of the opposed shell sections at an angle to each other'maximumstrength is obtained and all tendency to axial distortionis-eliminated.The laying of the- {designated as 10. Said halves abut longimesa-me rsstrips of the layers of one shell section at an angle to each other isinstrumental in giving the required strength and the layin of the stripsof the corresponding layers 0 the opposed shell section isinstrumental'in obviat only been overcome heretofore by the provision ofa third or reinforcing layer of strips. The twisting tendency is dueentirely to the continuity of the strips and'not to the arrangement.followed. Herein, on the other hand, the strips are discontinuous andthe twisting. tendency that might pos= sibly be set up 1n one'shellsection, is counter-acted and completely off-set by the oppositetwisting tendency set up in the abutting shell section.

Such fuselage construction is not only better because of theelimination-of the twisting tendency but better aero-dynamically becauseof the reduction in weight. The use of a third or reinforcing layer iscompletely eliminated without a sacrifice of strength, The improvedfuselage moreover involves a 'big saving of material since strips ofwood heretofore considered scrap may be. readily or filler 22 ismounted. Said core or filler is fastened to the jig by any suitablemeans. Preferably the core or filleris adapted to the half only of thefuselage. The particular edge to edge.

half is Immaterial, it may be either right, left, upper or lower. Asherein explained the fuselage is divided into right and left halves.Upon the rounded working face of the core or filler 22 the shellsections are.

built. In constructing them, the strips which afterward constitute theinner layer of strips, are laid diagonally over the core The edges mayor may. not abut. In Figs. 1 to 5 inclusive the edges are shown asabutting and in Figs. 6, (the modification) the edges abut only at theends of the strips. To, abut them requires an increased amount of laborsince it is necessary, due to the tapering form of the core to plane offthe edges of adjacent strips whereas in of the shell.

the modification a wicker or' latticed-work type of fuselage shell isproduced. The ends of the strips after the edges thereof have beentrimmed off as required are attached to the side rails 21 of the jig 20.In this way they are held in place temporarily. Upon the completion ofthe first'layer, or even before it is complete, the laying of the secondlayer may be started. In laying'the, second layer (afterward the outerlayer) the strips are laid diagonally in the opposite direction to thestrlps of the first or inner layer. They too are carried beyond the flator non-working face 'of the core to be temporarily fastened to the siderails'21 of the igJ Before laying the second layer, however, the outerface ofthe inner layer is I given an application of glue.

Upon hardening the glue holds the layers together, or its equivalent. Ifdesired, the strips of wood before their application may be bathed inglue including glycerin as an. ingredient since this treatment of thewood tends to minimizethe possibility of all fracture and splittingduring their application. The glycerin in the glue softens the wood andeliminates subsequent warping.

After the two layers-of strips are glued together and after the glue isproperly set or congealed the complete shell section is removed from thecore 22 by cutting it along lines at each side ofthe jig 20 intermediatethe outside bottom edges of the core 22 and the outside top edges of therails 21. The stubs or waste 'inaterial of the strips which are stillfastened to the rails 21 may be then removed to admit of theconstruction of a second shell section upon the same core.

It is not essential, however, that the same core be used in the erectionof both halves A similar or a different formof core may be used for thesecond half. Where the halves are symmetrical however, it is preferredthat the one core be used since it is possible to proceed with theconstruction of the second half after the re-' cent. In fastening themtogetherstringers 23 are provided. These stringers extend throughout thefull length of the body upon the inside of the shell. The abutting edgesof the shell sections are screwed to the stringers as intimated at 24.Before fasten ing the edges of the abutting shell sections together,however, they should be planed down in order that a perfect fit maybeprovided.

In the assembly of the fuselage a jig orstand 30 is provided. The topface of this cramped position.

jig is recessed or cut away to receive and snugly engage one of thecompleted shell sections or halves. The completed shell section or halfis placed on'the jig with its open side uppermost and is held in placeby its snug engagement with the recessed top face of the jig. \Vhile inthis position a substantial. portion of the interior equipment of thefuselage is assembled. Such equipment includes an engine bed 31,suitable frames 32, 'a fuel tank (not shown), etc. Not only-can suchequipment he readily positioned within the half section of the fuselagewhen thus supported upon the jig but because of its accessibility suchequipment can be finally and permanently fastened in place. Heretofore,as explained, the rapid assembly of the interior fuselage equipment infuselages or nacelles of the monocoque. type has been greatly impeded asa resultof the inaccessibility of the fuselage interior. To assemblesuch equipment in the completed monocoque shell requires that theworkman or workmen work from the inside and accordingly in a more orless As a result of the improved method of assembly this objectionablefeature is entirely overcome since substantially the greater portion of,if not all,

of the interior equipment can be completely and finally assembled beforethe shell sections constituting the completed shell are fastenedtogether. After the installation of the fuselage equipment the secondshell section is fastened in place with its open side adjacent the openside of the shell section resting on the jig and with its longitudinaledges in firm abutting engagement with the corresponding edges of saidfirst mentioned shell section or half.

If, as herein disclosed, the shell is divided vertically the shellsections. during the assembly of the body, are laid edge to edge and theinterior fuselage equipment placed in the shell section directlysupported by the jig, not in an upright position but in a positioncorresponding with the division line of the shell. If the shell isdivided transversely, and this is entirely practical, the interiorequipment may be assembled in an upright position. The reason, however,for

Y dividing the shell vertically is that divided in this way greaterstrength is obtained.

It will be noted that in the assembly no core or filler'is used. One ofthe shell sections merely rests upon a jig with'its open side up and isnot moved from this position until the fuselage is completed and theinterior. equipment finally installed. Another 60- advantage inconsequence of, the methods herein practised is the advantage derivedthrough the saving of time. Obviously upon the! completion of the'firstshell section, workmen other than those engaged in the construction ofthe second shell section may be immediately put to work installing theinterior equipmentwithout holding up or delaying the completion of thesecond shell section or half. Furthermore, even where but oneconstructi6n jig is provided there is no let up or hold up in the worksince the work resulting in the finished product may be continuouslycarried on.

Vhile I have described my invention in detail in its present preferredembodiment, it will be obvious to those skilled in the art afterunderstanding my invention, that various changes and modifications maybe made therein without departing from the spirit or scope thereof. Iaim in the appended claims to cover all such modifications and changes.

lVhat is claimed is:

1. The method of assembling airplane bodies of the monocoque type whichconsists in first providing a suitable jig or stand, next placingthereon a given section of the outer shell of the body, next insertingwithin the open side of the shell section a substantial portion of theinterior equipment of the body and thereafter placing over and upon theexposedequipment of the body a second shell section, which, inconjunction with the first mentioned shell section completes'the outershell of the body.

2. The method of assembling airplane bodies of the monocoque type whichconsists in first providing a suitable jig or stand, next placingthereon, open side up, a given section of the outer shell of the body,next inserting within the open side of the hull section a substantialportion of the interior equipment of the body, and thereafter plac 3.The method of assembling airplane bodies of the monocoque type whichconsists in first providing an upright jig or stand,

next placing thereon a half section of the outer shell of the body, nextinserting within the open side of the half sect1 on a substantialportion of the interior equlpment of the body, next placing over andupon the exposed equipment of the body theremaining half section which,in conjunction with the first mentioned shell section completes theouter shell of the body, and thereafter fastening the two shell-sectionstogether.

4. The method of constructing airplane in first providing a core or formover and upon which a given section ofthe outer shell is formed, nextremoving the complete shell section in the form given it by the core,next shaping and forming a second shell section over and upon the sameor similar core, next removinglthe last mentloned shell bodies of themonocoque type which consists section in the form given it by the core,and thereafter fastening thetwo shell sections together with their opensides adjacent.

5. The method of constructing airplane bodies of the monocoque typewhich consists in first providing a core or form over and upon which ahalf section of the outer shell is formed, next removing the'completehalf section in the form given it by the core, next core, next removingthe second mentioned shaping and forming the remaining half section in asimilar manner and by the use of the same or similar core, next removingthe last mentioned half section in the form given it by the core andthereafter fastening the two shell sections together with their opensides adjacent.

6. The method of. constructing monocoque shells for airplane bodieswhich consists in first providing a core or form of the size.

and shape in cross section approximately the same of a size and shape incross section of one-half of the airplane body, next spirally wrappingthereover and fastening shell section in the form given it by the core,thereafter fastening the two shell sections together with their opensides adjacent and the longitudinal edges thereof in engagement one withthe other.

7. The method of constructing monocoque shells for airplane bodies whichconsists in first providing a core or form of a size and shape in crosssection approximately the same as the size and shape in cross sectionofv one-half of the airplane body, next spirally wrapping thereover andfastening in place a plurality of-strips, next spirally wrapping in theopposite" direction and gluing in place over and upon the firstmentioned strips a second series of strips, next removing the shellsection thus formed from the core or filler, next shaping andconstructing a'second shell section in the same manner as the firstmentioned shell section, using either the same core or a core havin ashape in cross section approximately the same as the size and shape incross section as the remaining half of the airplane body, next removingthe last mentioned shell section in the form given it by the core andthereafter fastening the two shell sections together with their opensides adjacent and their longitudinal edges in abutting contact witheach other. e

8. The method of constructing monocoque shells which consists in firstproviding a core or form of a size and shape in cross sectionapproximately the same as the size and shape in cross section ofone-half of the air- 7 plane body, next spirally wrapping thereover aplurality of strips, the ends of the strips. being extended beyond theopposite longitudinal edges of the core where they are fastened,next'spirally wrapping in the opposite direction and glulng in placeoverand upon the first mentioned strips a second series of strips, nextremoving the shell section thus formed from the core or filler andcutting oil such portions thereof as ex tend beyond the longitudinaledges ofv the core, next shaping and constructing a second shell sectionin the same manner as the first mentioned shell section, using eitherthe same or asimilar core, next removing the second shell section in theform given it by the core and thereafter fastening the two shellsections together with their open sides adjacent and their oppositelongitudinal edges in abutting engagement with each other.

In testimony whereof I hereunto afiix my signature. 7

WHLIAM L. GILMORE-

